WO2000071880A3 - Simplified high-efficiency propulsion system - Google Patents

Simplified high-efficiency propulsion system Download PDF

Info

Publication number
WO2000071880A3
WO2000071880A3 PCT/US2000/012658 US0012658W WO0071880A3 WO 2000071880 A3 WO2000071880 A3 WO 2000071880A3 US 0012658 W US0012658 W US 0012658W WO 0071880 A3 WO0071880 A3 WO 0071880A3
Authority
WO
WIPO (PCT)
Prior art keywords
combustion chamber
rotor assembly
centripetal
propulsion system
coriolis
Prior art date
Application number
PCT/US2000/012658
Other languages
French (fr)
Other versions
WO2000071880A2 (en
WO2000071880B1 (en
Inventor
James A Bowery
Roger E Gregory
Original Assignee
James A Bowery
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by James A Bowery filed Critical James A Bowery
Priority to AU67467/00A priority Critical patent/AU6746700A/en
Priority to EP00955238A priority patent/EP1185778A2/en
Publication of WO2000071880A2 publication Critical patent/WO2000071880A2/en
Publication of WO2000071880A3 publication Critical patent/WO2000071880A3/en
Publication of WO2000071880B1 publication Critical patent/WO2000071880B1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/66—Combustion or thrust chambers of the rotary type

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

A rocket engine has a rotor assembly (10) with an ultracentrifugal liquid pump (28) arranged around a combustion chamber (52) so as to provide both forced convective and Coriolis-effect and centripetal-acceleration enhanced free convective regenerative cooling to the combustion chamber while pressurizing the liquid propellant. The combustion chamber may be structured to rotate together with the pump to provide Coriolis effect and centripetal acceleration enhanced combustion. The rotor assembly is driven directly by a tangential component of the primary thrust vector by means of tilted nozzles (16) or by vanes, fluted, or other reaction surfaces.
PCT/US2000/012658 1999-05-14 2000-05-08 Simplified high-efficiency propulsion system WO2000071880A2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU67467/00A AU6746700A (en) 1999-05-14 2000-05-08 Simplified high-efficiency propulsion system
EP00955238A EP1185778A2 (en) 1999-05-14 2000-05-08 Simplified high-efficiency propulsion system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/312,585 US6212876B1 (en) 1999-05-14 1999-05-14 Simplified high-efficiency propulsion system
US09/312,585 1999-05-14

Publications (3)

Publication Number Publication Date
WO2000071880A2 WO2000071880A2 (en) 2000-11-30
WO2000071880A3 true WO2000071880A3 (en) 2001-01-18
WO2000071880B1 WO2000071880B1 (en) 2001-03-01

Family

ID=23212136

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2000/012658 WO2000071880A2 (en) 1999-05-14 2000-05-08 Simplified high-efficiency propulsion system

Country Status (5)

Country Link
US (1) US6212876B1 (en)
EP (1) EP1185778A2 (en)
AU (1) AU6746700A (en)
TW (1) TW479107B (en)
WO (1) WO2000071880A2 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030089434A1 (en) * 2000-11-20 2003-05-15 Flynn Thomas M. Method and apparatus for the preparation and usage of a cryogenic propellant or explosive system
MXPA04009982A (en) * 2002-04-11 2006-02-22 Richard A Haase Water combustion technology-methods, processes, systems and apparatus for the combustion of hydrogen and oxygen.
KR20040023396A (en) * 2002-09-11 2004-03-18 현대모비스 주식회사 Design method for swirl test injector
US6807805B2 (en) * 2003-03-11 2004-10-26 United Technologies Corporation Hypergolic fuel system
US20110017874A1 (en) * 2007-11-26 2011-01-27 Clearvalue Technologies, Inc. Means of fuel and oxidizer storage
US9650997B2 (en) 2013-03-05 2017-05-16 John Bossard Rotary turbo rocket
RU2554126C1 (en) * 2013-12-18 2015-06-27 Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" Combined engine unit of rocket pod
UA108043C2 (en) * 2013-12-30 2015-03-10 Oleksandr Illarionovych Yudin Continuous-flow rotary heater
CN114412663B (en) * 2021-12-23 2023-08-29 北京航天动力研究所 Integrated liquid rocket engine thrust chamber top cover structure

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2523011A (en) * 1947-11-01 1950-09-19 Daniel And Florence Guggenheim Cooling and feeding means for rotating combustion chambers
US2536599A (en) * 1948-01-02 1951-01-02 Daniel And Florence Guggenheim Steam-operated rotating combustion chamber

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2519878A (en) * 1946-07-31 1950-08-22 Carold F Bjork Rocket projectile
US2516462A (en) * 1946-10-17 1950-07-25 Daniel And Florence Guggenheim Double jacket means for feeding two liquids to a rotating combustion chamber
US3553964A (en) * 1968-01-15 1971-01-12 Thiokol Chemical Corp Propellant feed system for rocket powerplants

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2523011A (en) * 1947-11-01 1950-09-19 Daniel And Florence Guggenheim Cooling and feeding means for rotating combustion chambers
US2536599A (en) * 1948-01-02 1951-01-02 Daniel And Florence Guggenheim Steam-operated rotating combustion chamber

Also Published As

Publication number Publication date
WO2000071880A2 (en) 2000-11-30
EP1185778A2 (en) 2002-03-13
WO2000071880B1 (en) 2001-03-01
AU6746700A (en) 2000-12-12
TW479107B (en) 2002-03-11
US6212876B1 (en) 2001-04-10

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